Cargo compartment mounting assembly, cargo compartment and unmanned aerial vehicle
Patent Information
- Application Number
- CN202521929004.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-08
- Publication Date
- 2026-10-20
- Estimated Expiration
- 2035-09-08
AI Technical Summary
[0003]相关技术中，利用绑定在无人机的机身外部或集成在无人机的机身内部的货舱收纳货物，然而该设置方式，由于货舱无法拆卸，导致装卸货费时费力，进而影响运营效率
[0040]本申请提供的货舱挂载总成包括第一横梁、第二横梁、移动机构、第一钩挂连接件和第二钩挂连接件，其中，第一横梁和第二横梁连接在无人机本体上，第一钩挂连接件和第二钩挂连接件连接在货舱上，并且，移动机构能够带动货舱在支撑面上移动。具有本申请中的货舱挂载总成的无人机在装卸货物时，首先，利用货舱挂载总成中的移动机构，带动货舱沿脱离挂载的方向移动，进而将货舱自无人机本体上卸载下来。之后，可继续利用上述移动机构带动货舱移动至货物装卸点进行货物的装卸。货物装卸完成后，继续利用移动机构带动货舱移动，并在移动过程中调整移动方向，使货舱挂载总成中的第一钩挂连接件和第二钩挂连接件分别与第一横梁和第二横梁钩挂连接，以将货舱挂载于无人机本体上。
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Figure CN224868594U_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of aircraft technology, specifically to a cargo hold mounting assembly, a cargo hold, and an unmanned aerial vehicle (UAV). Background Technology
[0002] Drone delivery is becoming increasingly common. As the business matures, the cargo capacity is gradually increasing, with the single-trip cargo weight requirement rising rapidly from a few kilograms to tens of kilograms. The packaging shapes of express goods are also becoming more diverse.
[0003] In related technologies, cargo is stored using a cargo compartment that is attached to the outside of the drone's fuselage or integrated inside the drone's fuselage. However, this setup results in time-consuming and labor-intensive loading and unloading because the cargo compartment cannot be disassembled, which in turn affects operational efficiency. Utility Model Content
[0004] In view of this, this application provides a cargo hold mounting assembly that allows the cargo hold to be detachably mounted on the outside of a UAV. Furthermore, when it is necessary to mount or unmount the cargo hold, it is only necessary to push the cargo hold relative to the UAV in a specific direction, making the mounting or unmounting of the cargo hold convenient and quick. In addition, this application also provides a cargo hold that can be mounted on a UAV using the aforementioned cargo hold mounting assembly, and a UAV including the aforementioned cargo hold mounting assembly.
[0005] To achieve the above objectives, this application provides the following technical solution:
[0006] A cargo hold mounting assembly is suitable for mounting a cargo hold onto the body of a drone; the cargo hold mounting assembly includes:
[0007] The first and second crossbeams are both fixedly connected to the UAV body;
[0008] A moving mechanism is used to move the cargo compartment on the support surface;
[0009] Both the first hook connector and the second hook connector are fixedly connected to the cargo hold;
[0010] The first crossbeam is located on the travel path of the first hook connector, and the second crossbeam is located on the travel path of the second hook connector. As the cargo hold moves on the support surface, the first hook connector and the second hook connector can be hooked and connected to the first crossbeam and the second crossbeam, respectively.
[0011] Optionally, in the direction of movement of the cargo hold, the first crossbeam and the second crossbeam are spaced apart, and the distance between the second crossbeam and the support surface is greater than or equal to the distance between the top of the first hook connector and the support surface.
[0012] Optionally, a first protective member is detachably connected to the first crossbeam, and the first protective member is used to isolate the first crossbeam from the first hook connector; and / or
[0013] The second crossbeam is detachably connected to a second protective component, which is used to isolate the second crossbeam from the second hook connector.
[0014] Optionally, a limiting component is included, the limiting component comprising:
[0015] A first limiting member is disposed on the first crossbeam and is used to limit the movement of the first hook connector along the length of the first crossbeam; and / or
[0016] The second limiting member is arranged on the second crossbeam and is used to limit the movement of the second hook connector in the length direction of the second crossbeam.
[0017] Optionally, the first limiting member has a first guide ramp; when the cargo hold moves, the first guide ramp is used to guide the first hook connector to the position where the first crossbeam is used to connect the first hook connector; and / or
[0018] The second limiting member has a second guide ramp; when the cargo hold moves, the second guide ramp is used to guide the second hook connector to the position where the second crossbeam is used to connect the second hook connector.
[0019] Optionally, both the first hook connector and the second hook connector include a hook, and the second hook connector further includes:
[0020] A locking mechanism, connected to the hook, is capable of closing the opening of the hook to confine the second beam within the hook groove.
[0021] Optionally, the locking mechanism includes:
[0022] An anti-detachment component is hinged to the hook and located at the opening of the hook. The anti-detachment component has a first state and a second state. In the first state, the anti-detachment component closes the opening of the hook to confine the second crossbeam within the hook groove. In the second state, the anti-detachment component avoids the opening of the hook to allow the second crossbeam to enter and exit the hook groove.
[0023] A locking element is connected to the hook and is connected to the anti-detachment element in the first state of the anti-detachment element, so that the anti-detachment element is maintained in the first state.
[0024] Optionally, the anti-detachment component includes:
[0025] The anti-slip component body is connected to the hook and can also be connected to the locking component;
[0026] The limiting bolt is threadedly connected to the anti-detachment component body and can abut against the second crossbeam when the anti-detachment component is in the first state.
[0027] A cargo hold, wherein the cargo hold has a first mounting structure at the bottom and a second mounting structure at the top; the first mounting structure is used to mount a moving mechanism of a cargo hold mounting assembly, and the second mounting structure is used to mount a first hook connector and a second hook connector of the cargo hold mounting assembly; the cargo hold mounting assembly is any one of the cargo hold mounting assemblies described above.
[0028] Optionally, the cargo hold includes:
[0029] Cargo hold frame, comprising multiple carbon fiber tubes that are staggered and connected;
[0030] The skin covers the outside of the cargo hold frame to form an enclosed loading space.
[0031] Optionally, the cargo hold has guide arc surfaces at both ends along its length.
[0032] A drone, comprising:
[0033] The drone itself;
[0034] Cargo hold, as described in any of the above-mentioned items;
[0035] The cargo hold mounting assembly is any one of the cargo hold mounting assemblies described above, and is used to mount the cargo hold onto the UAV body.
[0036] Optionally, the drone body includes:
[0037] Organism;
[0038] The landing gear is connected to the lower part of the fuselage and is used to support the fuselage; the landing gear includes a front landing gear and a rear landing gear that are spaced apart, and both the front landing gear and the rear landing gear include a support crossbeam connected to the fuselage, and support vertical beams located at both ends of the support crossbeam;
[0039] Wherein, the first crossbeam of the cargo hold mounting assembly is the support crossbeam of the front landing gear; and / or the second crossbeam of the cargo hold mounting assembly is the support crossbeam of the rear landing gear.
[0040] The cargo hold mounting assembly provided in this application includes a first crossbeam, a second crossbeam, a moving mechanism, a first hook connector, and a second hook connector. The first and second crossbeams are connected to the UAV body, and the first and second hook connectors are connected to the cargo hold. The moving mechanism can move the cargo hold on a supporting surface. When loading and unloading cargo, the UAV equipped with the cargo hold mounting assembly of this application first uses the moving mechanism in the cargo hold mounting assembly to move the cargo hold in the direction of detachment, thereby unloading the cargo hold from the UAV body. Afterward, the moving mechanism can continue to move the cargo hold to the cargo loading / unloading point for loading and unloading. After loading and unloading, the moving mechanism continues to move the cargo hold, and the direction of movement is adjusted during the movement so that the first and second hook connectors in the cargo hold mounting assembly are hooked and connected to the first and second crossbeams respectively, thereby mounting the cargo hold onto the UAV body.
[0041] As described above, the cargo hold mounting assembly of this application allows the cargo hold to be detachably connected to the UAV body. This means that during loading and unloading, the cargo hold can detach from the UAV body and move to the loading / unloading point, thus avoiding long transfer distances during loading and unloading. Furthermore, once the cargo hold is detached from the UAV body, the UAV body can avoid interfering with the loading and unloading process, facilitating faster loading and unloading and improving operational efficiency. In addition, as mentioned above, when mounting or unloading the cargo hold using the cargo hold mounting assembly of this application, it is only necessary to push the cargo hold relative to the UAV body in a specific direction. Mounting or unloading the cargo hold is convenient and quick, further improving loading and unloading efficiency. Attached Figure Description
[0042] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.
[0043] Figure 1 A schematic diagram of the structure of a drone provided in an embodiment of this application;
[0044] Figure 2 A schematic diagram of a cargo hold mounting assembly provided in an embodiment of this application;
[0045] Figure 3 for Figure 2 Front view of the cargo hold mounting assembly;
[0046] Figure 4 for Figure 2 Side view of the cargo hold mounting assembly;
[0047] Figure 5 for Figure 2 A top view of the cargo hold mounting assembly.
[0048] Figure 6 for Figure 2 A magnified view of a portion of region A in the middle;
[0049] Figure 7 for Figure 2 A magnified view of a portion of region B in the middle;
[0050] Figure 8 A schematic diagram of a cargo hold frame provided for an embodiment of this application;
[0051] Figure 9 A schematic diagram of a first hook connector provided in an embodiment of this application;
[0052] Figure 10 A schematic diagram of a second hook connector provided in an embodiment of this application;
[0053] Figure 11 for Figure 9 A schematic diagram of the internal structure of the second hook connector.
[0054] exist Figures 1-11 middle:
[0055] 100 - Unmanned Aerial Vehicles (UAVs);
[0056] 1-UAV body, 2-Cargo compartment, 3-First crossbeam, 4-Moving mechanism, 5-Handle, 6-First hook connector, 7-Second hook connector, 8-First limiting component, 9-First protective component, 10-Second limiting component, 11-Second protective component, 12-Clamp;
[0057] 101-Airframe, 102-Landing gear, 201-Cargo hold frame, 202-Guide arc surface, 203-Rib, 204-Frame, 205-Tube beam, 701-Second hook, 702-Locking component, 703-Anti-detachment component;
[0058] 7031 - Anti-detachment component body, 7032 - Limit bolt. Detailed Implementation
[0059] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0060] like Figure 1 As shown in the figure, this application discloses a drone 100, which includes a drone body 1, a cargo compartment 2, and a cargo compartment mounting assembly (not shown in the figure).
[0061] The UAV body 1 is the main carrier of the UAV 100 used to achieve its flight function. For example... Figure 1 As shown, the main body of the drone 100 includes a fuselage 101 and a landing gear 102.
[0062] The landing gear 102 is located below the fuselage 101 and is used to support the fuselage 101.
[0063] The landing gear 102 can be fixedly installed under the fuselage 101. That is, the landing gear 102 is a non-retractable structure and is fixed to the underside of the fuselage 101 by welding or by fasteners (such as threaded fasteners).
[0064] In this configuration, the drone 100 does not need a drive structure for retracting and extending the landing gear 102, which helps to reduce the cost and weight of the drone 100.
[0065] The landing gear 102 can also be movably connected to the lower part of the fuselage 101, that is, the landing gear 102 is retractably disposed under the fuselage 101. In an exemplary embodiment, the landing gear 102 can be configured as a telescopic structure, and the landing gear 102 can retract into the fuselage 101 during the flight mission of the UAV 100. Alternatively, the landing gear 102 can also be configured as a flip-up structure, and the landing gear 102 can flip to the retracted position during the flight mission of the UAV 100.
[0066] In this configuration, when the drone 100 is performing a flight mission, the landing gear 102 is in the retracted position, which helps to reduce wind resistance.
[0067] Furthermore, the landing gear 102 includes a front landing gear and a rear landing gear spaced apart.
[0068] The structure of the front landing gear can be the same as or different from that of the rear landing gear; this application does not impose any specific limitations on this. For ease of description, the structure of the landing gear 102 will be explained below using the example that the front landing gear structure is the same as that of the rear landing gear.
[0069] The landing gear 102 includes a support crossbeam and a support vertical beam.
[0070] The support beam can be connected to the body 101.
[0071] For example, the support beam has multiple connection structures (e.g., connection holes) arranged along its length and is connected to the body 101 through these connection structures.
[0072] The supporting vertical beams are located at both ends of the supporting horizontal beams.
[0073] The supporting crossbeam and supporting vertical beam can be a single piece, or they can be independent components that are fixedly connected.
[0074] One or more supporting vertical beams may be installed at either end of the supporting horizontal beam. This application does not make specific limitations on this, and adaptive design can be carried out as needed during implementation.
[0075] In one exemplary implementation, such as Figure 2 and Figure 3 As shown, the landing gear 102 is a single piece, formed by bending tubing.
[0076] It should be understood that the landing gear 102 described above, including the support crossbeam and the support vertical beam, is only an exemplary implementation of the landing gear 102, but this application is not limited thereto. For example, the landing gear 102 may also include only the support vertical beam, that is, the landing gear 102 may be a plurality of support vertical beams directly connected to the underside of the fuselage 101.
[0077] Cargo compartment 2 is an additional functional module of UAV 100, mainly used for loading cargo, and is an extension device of UAV 100.
[0078] In some embodiments, cargo hold 2 includes cargo hold frame 201 and skin.
[0079] Cargo hold frame 201 is the supporting frame for cargo hold 2.
[0080] like Figure 8 As shown, the cargo hold frame 201 includes multiple cross-shaped and connected tubular beams 205.
[0081] The different pipe beams 205 mentioned above can be fixed by welding, or they can be connected by connectors (such as tee connectors). This application does not make specific limitations on this, and adaptive design can be carried out as needed during implementation.
[0082] Furthermore, the aforementioned tube beam 205 is preferably a carbon fiber tube; in this way, since the carbon fiber tube is lighter, it is beneficial to reduce the weight of the cargo hold 2 itself, thereby increasing the loading space of the cargo hold 2 and increasing the cargo capacity of the cargo hold 2. Of course, this is not intended to limit this application. When the weight of the cargo hold 2 does not need to be considered, or when there are other considerations (such as manufacturing costs), the aforementioned tube beam 205 can also be a metal tube or the like.
[0083] Continue as Figure 8 As shown, the bottom of cargo compartment 2 is provided with multiple ribs 203 for supporting the cargo in the loading space.
[0084] Multiple ribs 203 can be arranged in parallel at the bottom of the cargo hold 2, or they can be arranged in an alternating manner at the bottom of the cargo hold 2. This application does not specifically limit this arrangement. However, it is more preferred that the multiple ribs 203 be arranged in an alternating manner at the bottom of the cargo hold 2. In this way, the different ribs 203 support each other, which helps to improve the supporting capacity of the ribs 203.
[0085] In one exemplary embodiment, multiple cross-shaped ribs 203 are arranged at the bottom of the cargo hold 2 and connected to the tube beam 205. This arrangement, on the one hand, helps to improve the load-bearing capacity of the cargo hold 2 and prevent cargo from sagging; on the other hand, the cross-shaped ribs 203 form multiple stable triangular structures at the bottom of the cargo hold 2, which in turn helps to improve the structural stability of the cargo hold 2.
[0086] The skin is a thin layer of material covering the outside of the cargo hold frame 201, which is used to form the outer surface of the cargo hold 2 to form an enclosed loading space inside the cargo hold 2.
[0087] The skin can be made of Oxford cloth. Compared with metal materials such as aluminum alloy, Oxford cloth is cheaper and lighter, which helps to reduce costs. At the same time, it helps to reduce the weight of the cargo hold 2 itself, thereby increasing the loading space and cargo capacity of the cargo hold 2.
[0088] Furthermore, in some implementations, such as Figure 4 As shown, the upper surface of the skin has a C-shaped opening, which is used for loading and unloading goods and is opened and closed by a zipper structure.
[0089] As can be understood, as mentioned above, the skin covers a frame structure. Given this, when the cargo volume is small, it may leak through the gaps between adjacent tubular beams 205 of the cargo hold frame 201. In this case, the skin needs to directly participate in load-bearing. In this embodiment, the opening is located on the upper surface of the skin. Since the upper surface of the skin is a non-load-bearing surface, this helps to avoid insufficient load-bearing capacity of the skin due to the opening.
[0090] In some embodiments, the cargo compartment 2, which accommodates cargo, is a cuboid, and both ends of the cargo compartment 2 along its length have guide arc surfaces 202. This helps to reduce the flight drag of the UAV 100, thereby increasing the flight range of the aircraft.
[0091] In an exemplary implementation, such as Figure 4 and Figure 5 As shown, cargo hold 2 is tapered at both ends along its length. Specifically, as... Figure 8As shown, the cargo hold frame 201 has tapered skeletons 204 at both ends along its length direction. The skin is wrapped around the outside of the skeleton 204 to form a tapered flow guide structure, which is used to surround the surface of the tapered structure, namely the flow guide arc surface 202 at both ends of the cargo hold 2 along its length direction.
[0092] The cargo hold mounting assembly is a connection structure used to mount the cargo hold 2 onto the UAV 100.
[0093] like Figure 2 As shown, the cargo hold mounting assembly in this application includes a first crossbeam 3, a second crossbeam, a moving mechanism 4, a first hook connector 6, and a second hook connector 7.
[0094] Both the first crossbeam 3 and the second crossbeam are fixedly connected to the UAV 100.
[0095] More specifically, the first crossbeam 3 and the second crossbeam are both fixed to the underside of the body 101 of the UAV 100.
[0096] During implementation, the first crossbeam 3 and the second crossbeam may or may not be the same. This application does not make specific restrictions on this, and adaptive design can be carried out according to the specific situation during implementation.
[0097] Furthermore, as mentioned above, a landing gear 102 is provided below the fuselage 101 of the UAV 100, and in some embodiments, the landing gear 102 includes a support crossbeam and a support longitudinal beam. In this case, the first crossbeam 3 of the cargo hold mounting assembly can be the support crossbeam of the landing gear 102, and / or the second crossbeam of the cargo hold mounting assembly can be the support crossbeam of the landing gear 102. In this way, the cargo hold mounting assembly and the landing gear 102 share the crossbeam structure, which helps to reduce the number of crossbeam structures, thereby simplifying the structure and reducing the weight of the UAV 100.
[0098] In one exemplary implementation, such as Figure 2 As shown, the bottom of the fuselage 101 of the UAV 100 is provided with two landing gears 102 spaced apart along the length of the cargo hold 2. These two landing gears 102 have identical structures and each includes a support crossbeam and two support longitudinal beams, with the two longitudinal beams located at opposite ends of the support crossbeam. For ease of description, the two landing gears 102 will be referred to as the front landing gear and the rear landing gear, respectively. Continuing as... Figure 2 As shown, in this embodiment, the first crossbeam 3 of the cargo hold mounting assembly is connected between the two supporting longitudinal beams of the front landing gear, and the second crossbeam of the cargo hold mounting assembly is the supporting crossbeam of the rear landing gear. That is to say, in this embodiment, the first crossbeam 3 of the cargo hold mounting assembly is an independent structure connected to the landing gear 102, and the second crossbeam is the supporting crossbeam of the landing gear 102.
[0099] Furthermore, the first crossbeam 3 and the supporting longitudinal beam of the front landing gear can be connected by a non-removable method such as welding. Under this connection method, the connection between the first crossbeam 3 and the supporting longitudinal beam is more reliable.
[0100] Of course, the first crossbeam 3 can also be detachably connected to the support longitudinal beam of the front landing gear via a connector. With this connection method, the first crossbeam 3 is detachable, which is more conducive to the maintenance, upkeep, and replacement of the first crossbeam 3 and related structures on the first crossbeam 3.
[0101] In an exemplary implementation, such as Figure 6 As shown, the first crossbeam 3 and the supporting longitudinal beam are connected by clamps 12. In this embodiment, clamps 12 are used as connecting parts, so that the supporting longitudinal beam will not be damaged during the connection process between the first crossbeam 3 and the supporting longitudinal beam.
[0102] The moving mechanism 4 is used to move the cargo compartment 2 on the supporting surface. This supporting surface is the plane used to park the drone 100; for example, the supporting surface can be the ground.
[0103] The mobile mechanism 4 can be an independent vehicle with a carrying function. For example, the mobile mechanism 4 can be a flatbed trolley, and the cargo compartment 2 can be placed on the carrying platform of the flatbed trolley.
[0104] The moving mechanism 4 can also be a mechanism connected to the cargo hold 2 to facilitate the movement of the cargo hold 2. For example, the bottom of the cargo hold 2 has a first mounting structure for mounting the aforementioned moving mechanism 4. Specifically, as... Figure 2 and Figure 4 As shown, the moving mechanism 4 includes multiple roller assemblies, each comprising a roller bracket and rollers rotatably connected to the roller bracket. Furthermore, the roller bracket is fixedly connected to the first mounting structure at the bottom of the cargo compartment 2.
[0105] Both the first hook connector 6 and the second hook connector 7 are fixedly connected to the cargo hold 2. For example, as shown... Figure 2 As shown, the top of the cargo hold 2 has a second mounting structure, which is used to install the first hook connector 6 and the second hook connector 7 of the cargo hold mounting assembly.
[0106] Furthermore, the first crossbeam 3 is located on the travel path of the first hook connector 6, and the second crossbeam is located on the travel path of the second hook connector 7. As the cargo hold 2 moves on the support surface, the first hook connector 6 and the second hook connector 7 can be hooked and connected to the first crossbeam 3 and the second crossbeam respectively.
[0107] When using the UAV 100 of this application to load and unload cargo, firstly, the moving mechanism 4 in the cargo hold mounting assembly is used to move the cargo hold 2 in the direction of detachment from the mounting, thereby unloading the cargo hold 2 from the UAV body 1. Afterwards, the moving mechanism 4 can be used to move the cargo hold 2 to the cargo loading / unloading point for loading and unloading cargo. After loading and unloading is completed, the moving mechanism 4 is used to move the cargo hold 2, and the direction of movement is adjusted during the movement so that the first hook connector 6 and the second hook connector 7 in the cargo hold mounting assembly are hooked and connected to the first crossbeam 3 and the second crossbeam respectively, so as to mount the cargo hold 2 onto the UAV body 1.
[0108] As described above, the cargo compartment 2 of the drone 100 in this application is detachably connected to the drone body 1 via a cargo compartment mounting assembly. This allows the cargo compartment 2 to move to the loading / unloading point during cargo loading and unloading. Furthermore, once the cargo compartment 2 is detached from the drone body 1, the drone body 1 can avoid interfering with the cargo loading / unloading process, thus facilitating faster cargo loading and unloading and improving operational efficiency. In addition, as mentioned above, when mounting or unloading the cargo compartment 2 using the cargo compartment mounting assembly in this application, it is only necessary to push the cargo compartment 2 relative to the drone body 1 in a specific direction. Mounting or unloading the cargo compartment 2 is convenient and quick, further improving cargo loading and unloading efficiency.
[0109] In some embodiments, such as Figure 2 and Figure 3 As shown, based on the fact that the moving mechanism 4 is provided to drive the cargo compartment 2 to move on the support surface, a handle 5 is provided on the side of the cargo compartment 2. The handle 5 can serve as a structure that facilitates the application of force during the movement of the cargo compartment 2.
[0110] In an exemplary embodiment, the handle 5 can be fixedly connected to the skin of the cargo compartment 2. This prevents the handle 5 from compromising the skin's seal.
[0111] In some embodiments, the first crossbeam 3 and the second crossbeam are spaced apart in the direction of movement of the cargo hold 2, and the distance between the second crossbeam and the support surface is greater than or equal to the distance between the top end of the first hook connector 6 and the support surface. This is to avoid interference between the first hook connector 6 and the second crossbeam during the movement of the cargo hold 2.
[0112] Of course, the above is only an exemplary implementation of the first crossbeam 3 and the second crossbeam, but this application is not limited to this. For example, in some other embodiments, the landing gear 102 of the UAV 100 can be set as a telescopic structure. In this way, by adjusting the height of the UAV body 1, interference between the crossbeam (the collective name for the first crossbeam 3 and the second crossbeam, hereinafter the same) and the connecting part (the collective name for the first hook connector 6 and the second hook connector 7, hereinafter the same) can be effectively avoided. In this case, the setting height of the first crossbeam 3 and the second crossbeam can be set to be the same height, or the first crossbeam 3 can be set to be higher than the second crossbeam, etc. Alternatively, when the moving direction of the cargo compartment 2 is consistent with the length direction of the crossbeam (at this time, the first crossbeam 3 and the second crossbeam are set in parallel), interference between the crossbeam and the connecting part can also be avoided.
[0113] In some embodiments, a first protective member 9 is detachably connected to the first crossbeam 3, and / or a second protective member 11 is detachably connected to the second crossbeam. More preferably, the first protective member 9 is detachably connected to the first crossbeam 3, and the second protective member 11 is detachably connected to the second crossbeam.
[0114] The first protective component 9 is used to isolate the first crossbeam 3 from the first hook connector 6. This prevents direct contact between the first hook connector 6 and the first crossbeam 3 when they are hooked together, thus avoiding wear on the first crossbeam 3 during loading and unloading of the cargo hold 2. In other words, the first protective component 9 in this embodiment is a structure used to protect the first crossbeam 3. Furthermore, since the first protective component 9 is detachably connected to the first crossbeam 3, it can be directly replaced when it becomes excessively worn. Replacing the first protective component 9 is significantly cheaper than replacing the crossbeam; therefore, this embodiment reduces maintenance costs by using the first protective component 9. In addition, as a load-bearing structure, preventing wear on the first crossbeam 3 also helps ensure the safety of the UAV 100 during cargo transport.
[0115] In one exemplary implementation, such as Figure 2 and Figure 6 As shown, the first crossbeam 3 is detachably connected to the support vertical beam of the landing gear 102 via clamp 12, and the first crossbeam 3 is detachably connected to the clamp 12. Based on this, the first protective component 9 is a protective sleeve fitted onto the first crossbeam 3; one end of the protective sleeve abuts against the clamp 12, and the other end abuts against a limiting pin. Thus, the clamp 12 and the limiting pin axially limit the protective sleeve, thereby preventing undesirable axial displacement of the protective sleeve connected to the first crossbeam 3.
[0116] In addition, it should be noted that the first protective component 9 can be a metal component, or it can be a rubber component with a certain shock absorption function, etc.
[0117] The second protective component 11 isolates the second crossbeam and the second hook connector 7. This prevents direct contact between the second hook connector 7 and the second crossbeam when they are hooked together, thus avoiding wear on the second crossbeam during loading and unloading of the cargo hold 2. In other words, the second protective component 11 in this embodiment is a structure used to protect the second crossbeam. Furthermore, since the second protective component 11 is detachably connected to the second crossbeam, it can be directly replaced when it becomes excessively worn. Replacing the second protective component 11 is significantly cheaper than replacing the crossbeam, meaning that this embodiment reduces maintenance costs by incorporating the second protective component 11. In addition, as a load-bearing structure, preventing wear on the second crossbeam also helps ensure the safety of the UAV 100 during cargo transport.
[0118] In one exemplary implementation, such as Figure 2 , Figure 7 and Figure 10 As shown, the second crossbeam is the support crossbeam of the landing gear 102. The second protective component 11 is a protective pad with a "U"-shaped end face that can cover the surface of the second crossbeam. Furthermore, the protective pad has multiple through holes so that it can be fixed to the support crossbeam by bolts or other structures during assembly.
[0119] In addition, it should be noted that the second protective component 11 can be a metal component, or it can be a rubber component or a polyurethane material component with a certain shock absorption function.
[0120] In some embodiments, the cargo hold mounting assembly includes a limiting component.
[0121] The limiting component includes a first limiting member 8 and / or a second limiting member 10. More preferably, the limiting component includes a first limiting member 8 and a second limiting member 10.
[0122] The first limiting member 8 is arranged on the first crossbeam 3 and is used to limit the movement of the first hook connector 6 in the length direction of the first crossbeam 3.
[0123] Preferably, the first limiting member 8 and the first crossbeam 3 are detachably connected. For example, the first limiting member 8 can be connected to the first crossbeam 3 via a threaded structure, or the first limiting member 8 can be limited and connected to the first crossbeam 3 via a limiting structure. Of course, this is not intended to limit the scope of this application. In some embodiments, the first limiting member 8 can also be fixedly connected to the first crossbeam 3 as needed.
[0124] Furthermore, the first limiting member 8 can be directly connected to the first crossbeam 3, or the first limiting member 8 can be indirectly connected to the first crossbeam 3 (that is, the first limiting member 8 is connected to the first crossbeam 3 through an intermediate connecting member). This application does not make specific limitations on this.
[0125] As shown above, by setting the first limiting member 8, the movement of the first hook connector 6 in the length direction of the first crossbeam 3 can be restricted. In this way, during the flight of the UAV 100, the cargo compartment 2 can be prevented from moving relative to the UAV 100 along the length direction of the first crossbeam 3, thereby preventing the center of gravity of the UAV 100 from shifting and improving the stability of the UAV 100 during flight.
[0126] The second limiting member 10 is arranged on the second crossbeam and is used to limit the movement of the second hook connector 7 in the length direction of the second crossbeam.
[0127] The second limiting member 10 and the second crossbeam are preferably detachably connected. For example, the second limiting member 10 can be connected to the second crossbeam via a threaded structure, or the second limiting member 10 can be connected to the second crossbeam via a limiting structure for limiting engagement. Of course, this is not intended to limit the scope of this application. In some embodiments, the second limiting member 10 can also be fixedly connected to the second crossbeam as needed.
[0128] Furthermore, the second limiting member 10 can be directly connected to the second crossbeam, or the second limiting member 10 can be indirectly connected to the second crossbeam (that is, the second limiting member 10 is connected to the second crossbeam through an intermediate connector). This application does not make specific limitations on this.
[0129] As shown above, by setting the second limiting member 10, the movement of the second hook connector 7 in the length direction of the second crossbeam can be restricted. In this way, during the flight of the UAV 100, the cargo compartment 2 can be prevented from moving relative to the UAV 100 along the length direction of the second crossbeam, thereby preventing the center of gravity of the UAV 100 from shifting and improving the stability of the UAV 100 during flight.
[0130] Furthermore, based on the limiting component including the first limiting member 8, in some embodiments, the first limiting member 8 has a first guide ramp. When the cargo compartment 2 moves, the first guide ramp is used to guide the first hook connector 6 to the position where the first crossbeam 3 is used to connect the first hook connector 6.
[0131] In other words, in addition to limiting the position, the first limiting member 8 in this embodiment also has a guiding function. In this way, during the process of moving the cargo compartment 2 to mount it on the UAV body 1, the first limiting member 8 can finely adjust the movement trajectory of the cargo compartment 2 and guide the first hook connector 6 to the position of the first crossbeam 3 for connecting the first hook connector 6. This helps to improve the connection accuracy between the first hook connector 6 and the first crossbeam 3 and simplifies the loading process of the cargo compartment 2.
[0132] In some exemplary implementations, such as Figure 2 As shown, there are two first hook connectors 6, which are distributed along the length of the first crossbeam 3. For ease of description, the surfaces of the first hook connectors facing each other are referred to as the first inner surfaces, and the surfaces of the first hook connectors facing away from each other are referred to as the first outer surfaces. The first limiting member 8 includes two symmetrically arranged limiting blocks, and the two first hook connectors are disposed between the two limiting blocks. The two limiting blocks can respectively engage with the first outer surfaces of different first hook connectors for limiting; thus, the first limiting member 8 limits the first hook connectors.
[0133] Furthermore, such as Figure 6 As shown, the limiting block is frustum-shaped and coaxially sleeved on the first protective member 9. During the loading of the cargo hold 2, the side of the limiting block can guide the first hook to the space between the two limiting blocks; that is, in this embodiment, the side of the limiting block is the first guide slope.
[0134] Of course, the above is only one exemplary implementation of the first limiting member 8, and this application is not limited thereto. For example, the first limiting member 8 may also include two trapezoidal blocks arranged symmetrically. Alternatively, the first limiting member 8 may also include multiple limiting block groups, each limiting block group including two limiting blocks arranged symmetrically on both sides of the first hook and hanger along the length direction of the first crossbeam 3.
[0135] Furthermore, based on the limiting component including the second limiting member 10, in some embodiments, the second limiting member 10 has a second guide ramp, which is used to guide the second hook connector 7 to the position where the second crossbeam is used to connect the second hook connector 7 when the cargo compartment 2 moves.
[0136] In other words, in addition to limiting the position, the second limiting member 10 in this embodiment also has a guiding function. In this way, during the process of moving the cargo compartment 2 to mount it on the UAV body 1, the second limiting member 10 can finely adjust the movement trajectory of the cargo compartment 2 and guide the second hook connector 7 to the position of the second crossbeam for connecting the second hook connector 7. This helps to improve the connection accuracy between the second hook connector 7 and the second crossbeam and simplifies the loading process of the cargo compartment 2.
[0137] In some exemplary implementations, such as Figure 2 As shown, two second hook connectors 7 are provided, distributed along the length of the second crossbeam. For ease of description, the opposing surfaces of the second hook connectors are referred to as the second inner surfaces, and the surfaces facing away from each other are referred to as the second outer surfaces. The second limiting member 10 includes two symmetrically arranged sheet metal parts, which are disposed between the two second hook connectors. The two sheet metal parts can respectively engage with the second inner surfaces of different second hook connectors for limiting; thus, the second limiting member 10 limits the second hook connectors.
[0138] Furthermore, such as Figure 7 As shown, the sheet metal part includes a limiting surface and a second guide slope that is inclined relative to the limiting surface. During the loading process of the cargo hold 2, the second guide slope can guide the movement of the second hook connector 7 so that the two sheet metal parts are located between the two second hook connectors 7.
[0139] In some embodiments, both the first hook connector 6 and the second hook connector 7 include hooks. Hooks are provided to enable hook connections between the first hook connector 6 and the first crossbeam 3, and between the first hook connector 6 and the second crossbeam.
[0140] For ease of description, the hook of the first hook connector 6 will be described as the first hook, and the hook of the second hook connector 7 will be described as the second hook 701.
[0141] In one exemplary implementation, such as Figure 9 As shown, the top of the hook groove of the first hook has a limiting groove, the shape and size of which are adapted to the outer peripheral surface of the first protective member 9. After the UAV 100 takes off, under the action of gravity, the first crossbeam 3 can be engaged in the aforementioned limiting groove, thus preventing the first hook connector 6 from moving relative to the first crossbeam 3 in the radial direction of the first crossbeam 3. This further improves the stability of the connection between the UAV body 1 and the cargo compartment 2.
[0142] The second hook 701 may be the same as or different from the first hook; this application does not make any specific restrictions on this.
[0143] Furthermore, in some embodiments, the second hook connector 7 also includes a locking mechanism connected to the second hook 701 and capable of closing the opening of the second hook 701 to confine the second crossbeam within the hook groove of the second hook 701. This prevents connection failure between the second hook connector 7 and the second crossbeam, thereby improving the reliability of the connection between the second hook connector 7 and the second crossbeam.
[0144] In some embodiments, the locking mechanism includes an anti-disengagement member 703 and a locking member 702.
[0145] The anti-detachment component 703 is hinged to the second hook 701 and located at the opening of the second hook 701. During implementation, the anti-detachment component 703 is rotated relative to the second hook 701 to open or close the slot. That is, in this embodiment, the anti-detachment component 703 has a first state and a second state. In the first state, the anti-detachment component 703 closes the opening of the second hook 701 to confine the second crossbeam within the hook slot. In the second state, the anti-detachment component 703 avoids the opening of the second hook 701 to allow the second crossbeam to enter and exit the hook slot. Furthermore, the anti-detachment component 703 can be switched between the first state and the second state by controlling its rotation relative to the second hook 701.
[0146] The locking member 702 is connected to the second hook 701 and is connected to the anti-detachment member 703 in the first state of the anti-detachment member 703 so that the anti-detachment member 703 is maintained in the first state.
[0147] The connection between the locking member 702 and the second hook 701 can be a hinge or a plug, etc. The specific design can be adapted according to the structure of the locking member 702 and the connection between the locking member 702 and the anti-detachment member 703.
[0148] In an exemplary implementation, such as Figure 11 As shown, the anti-detachment component 703 is elongated, with one end hinged to the second hook 701 along its length and the other end engaging with the locking component 702. The locking component 702 is hinged to the second hook 701 at its middle position, and its two ends are a first end and a second end, respectively. The first end is provided with a engaging structure (e.g., a engaging groove) that engages with the anti-detachment component 703, and the second end is connected to the second hook 701 by a spring. When the anti-detachment component 703 is in the first state and connected to the locking component 702, the spring is in a compressed state.
[0149] Furthermore, in some embodiments, the anti-detachment component 703 includes an anti-detachment component body 7031 and a limiting bolt 7032.
[0150] The anti-slip body 7031 is connected to the second hook 701 and can be connected to the locking member 702;
[0151] The limiting bolt 7032 is threadedly connected to the anti-detachment component body 7031 and can abut against the second crossbeam when the anti-detachment component 703 is in the first state. In this way, by adjusting the screw-in amount of the limiting bolt 7032, the limiting accuracy of the anti-detachment component 703 against the second crossbeam can be further improved.
[0152] Of course, the above is only a preferred embodiment of this application, but this application is not limited thereto. In specific implementation, the positioning accuracy of the anti-detachment component 703 on the second crossbeam can be guaranteed by controlling the hook groove accuracy of the second hook 701 of the second hook connector 7.
[0153] The basic principles of this application have been described above with reference to specific embodiments. However, it should be noted that the advantages, benefits, and effects mentioned in this application are merely examples and not limitations, and should not be considered as essential features of each embodiment of this application. Furthermore, the specific details disclosed above are for illustrative and facilitative purposes only, and are not limitations. These details do not limit the application to the necessity of employing the aforementioned specific details for implementation.
[0154] The block diagrams of devices, apparatuses, devices, and systems involved in this application are merely illustrative examples and are not intended to require or imply that they must be connected, arranged, or configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, devices, and systems can be connected, arranged, and configured in any manner. Words such as “comprising,” “including,” “having,” etc., are open-ended terms meaning “including but not limited to,” and are used interchangeably with them. The terms “or” and “and” as used herein refer to the terms “and / or,” and are used interchangeably with them unless the context clearly indicates otherwise. The term “such as” as used herein refers to the phrase “such as but not limited to,” and is used interchangeably with it.
[0155] It should also be noted that in the apparatus, equipment, and methods of this application, the components or steps can be disassembled and / or recombined. These disassemblies and / or recombinations should be considered as equivalent solutions of this application.
[0156] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use this application. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein can be applied to other aspects without departing from the scope of this application. Therefore, this application is not intended to be limited to the aspects shown herein, but rather to be accorded the widest scope consistent with the principles and novel features disclosed herein.
[0157] It should be understood that the qualifiers “first,” “second,” “third,” “fourth,” “fifth,” and “sixth” used in the description of the embodiments of this application are only used to more clearly illustrate the technical solutions and are not intended to limit the scope of protection of this application.
[0158] The above description has been given for purposes of illustration and description. Furthermore, this description is not intended to limit the embodiments of this application to the forms disclosed herein. Although numerous exemplary aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.
Claims
1. A cargo hold mounting assembly, characterized in that, Suitable for attaching cargo compartments to the drone body; The cargo hold mounting assembly includes: The first and second crossbeams are both fixedly connected to the UAV body; A moving mechanism is used to move the cargo compartment on the support surface; Both the first hook connector and the second hook connector are fixedly connected to the cargo hold; The first crossbeam is located on the travel path of the first hook connector, and the second crossbeam is located on the travel path of the second hook connector. As the cargo hold moves on the support surface, the first hook connector and the second hook connector can be hooked and connected to the first crossbeam and the second crossbeam, respectively.
2. The cargo hold mounting assembly according to claim 1, characterized in that, In the direction of movement of the cargo hold, the first crossbeam and the second crossbeam are spaced apart, and the distance between the second crossbeam and the support surface is greater than or equal to the distance between the top of the first hook connector and the support surface.
3. The cargo hold mounting assembly according to claim 1, characterized in that, A first protective member is detachably connected to the first crossbeam, and the first protective member is used to isolate the first crossbeam from the first hook connector; and / or The second crossbeam is detachably connected to a second protective component, which is used to isolate the second crossbeam from the second hook connector.
4. The cargo hold mounting assembly according to claim 1, characterized in that, Includes a limiting component, the limiting component comprising: A first limiting member is disposed on the first crossbeam and is used to limit the movement of the first hook connector along the length of the first crossbeam; and / or The second limiting member is arranged on the second crossbeam and is used to limit the movement of the second hook connector in the length direction of the second crossbeam.
5. The cargo hold mounting assembly according to claim 4, characterized in that, The first limiting member has a first guide ramp; when the cargo hold moves, the first guide ramp is used to guide the first hook connector to the position where the first crossbeam is used to connect the first hook connector; and / or The second limiting member has a second guide ramp; when the cargo hold moves, the second guide ramp is used to guide the second hook connector to the position where the second crossbeam is used to connect the second hook connector.
6. The cargo hold mounting assembly according to claim 1, characterized in that, Both the first hook connector and the second hook connector include a hook, and the second hook connector further includes: A locking mechanism, connected to the hook, is capable of closing the opening of the hook to confine the second beam within the hook groove.
7. The cargo hold mounting assembly according to claim 6, characterized in that, The locking mechanism includes: An anti-detachment component is hinged to the hook and located at the opening of the hook. The anti-detachment component has a first state and a second state. In the first state, the anti-detachment component closes the opening of the hook to confine the second crossbeam within the hook groove. In the second state, the anti-detachment component avoids the opening of the hook to allow the second crossbeam to enter and exit the hook groove. A locking element is connected to the hook and is connected to the anti-detachment element in the first state of the anti-detachment element, so that the anti-detachment element is maintained in the first state.
8. The cargo hold mounting assembly according to claim 7, characterized in that, The anti-detachment component includes: The anti-slip component body is connected to the hook and can also be connected to the locking component; The limiting bolt is threadedly connected to the anti-detachment component body and can abut against the second crossbeam when the anti-detachment component is in the first state.
9. A cargo hold, characterized in that, The cargo hold has a first mounting structure at the bottom and a second mounting structure at the top; the first mounting structure is used to install the moving mechanism of the cargo hold mounting assembly, and the second mounting structure is used to install the first hook connector and the second hook connector of the cargo hold mounting assembly; the cargo hold mounting assembly is the cargo hold mounting assembly according to any one of claims 1-8.
10. The cargo hold according to claim 9, characterized in that, The cargo hold includes: Cargo hold frame, comprising multiple carbon fiber tubes that are staggered and connected; The skin covers the outside of the cargo hold frame to form an enclosed loading space.
11. The cargo hold according to claim 9 or 10, characterized in that, The cargo hold has flow-guiding arc surfaces at both ends along its length.
12. A drone, characterized in that, include: The drone itself; The cargo hold is the cargo hold as described in any one of claims 9-11; The cargo hold mounting assembly is the same as any one of claims 1-8, and is used to mount the cargo hold onto the UAV body.
13. The UAV according to claim 12, characterized in that, The drone body includes: Organism; The landing gear is connected to the lower part of the fuselage and is used to support the fuselage; the landing gear includes a front landing gear and a rear landing gear that are spaced apart, and both the front landing gear and the rear landing gear include a support crossbeam connected to the fuselage, and support vertical beams located at both ends of the support crossbeam; Wherein, the first crossbeam of the cargo hold mounting assembly is the support crossbeam of the front landing gear; and / or the second crossbeam of the cargo hold mounting assembly is the support crossbeam of the rear landing gear.